Stand-off panel thermal protection system and method of fabricating the same

• US 9,878,809 B2
• Filed: 06/12/2015
• Issued: 01/30/2018
• Est. Priority Date: 06/12/2015
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Best, Michael J., Pinney, Thomas R., Embler, Jonathan D.
• Primary Examiner(s): Davis, Richard G
• Application Number:
  US14/738,314
• Publication Number:
  US 20160362199A1
• Time in Patent Office: 963 Days
• CPC Class Codes: B64G 1/14 Space shuttles reusable launch rockets B64G1/006
• CPC Class Codes: B64G 1/58 Thermal protection, e.g. heat shields
• CPC Class Codes: B64G 1/62 Systems for re-entry into the earth's atmosphere; Retarding or landing devices
• CPC Class Codes: F16B 33/006 Non-metallic fasteners using screw-thread

Abstract

A stand-off panel thermal protection system includes a sandwich panel comprising: a first ceramic matrix composite facesheet and a second ceramic matrix composite facesheet. A ceramic matrix composite core is positioned between the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet. The ceramic matrix composite core has a perimeter. The first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet extend past the perimeter to form a gap between the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet surrounding the ceramic matrix composite core. A plurality of orifices are formed through the sandwich panel. The thermal protection system further comprises a soft goods seal positioned in the gap; a plurality of insulation components; a plurality of stand-off brackets; and a plurality of fasteners positionable through the plurality of orifices to couple the sandwich panel to the plurality of brackets.

Claims

1. A stand-off panel thermal protection system, comprising:

a sandwich panel comprising;

a first ceramic matrix composite facesheet and a second ceramic matrix composite facesheet,

a ceramic matrix composite core positioned between the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet, the ceramic matrix composite core having a perimeter, the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet extending past the perimeter to form a gap surrounding the ceramic matrix composite core between the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet, and

a plurality of orifices formed completely through the sandwich panel;

a soft goods seal positioned in the gap;

a plurality of insulation components;

a plurality of stand-off brackets; and

a plurality of fasteners positionable completely through the plurality of orifices to couple the sandwich panel to the plurality of brackets.

2. The system of claim 1, wherein the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet comprise at least one material chosen from oxide ceramic matrix composites or non-oxide ceramic matrix composites.

3. The system of claim 1, wherein the ceramic matrix composite core is a truss core comprising at least one material chosen from oxide ceramic matrix composites or non-oxide ceramic matrix composites.

4. The system of claim 1, wherein the soft goods seal comprises woven ceramic fabric and alumina fibrous batting insulation.

5. The system of claim 1, wherein each of the plurality of standoff brackets comprise a ceramic matrix composite material or high temperature metallic material.

6. The system of claim 1, wherein the plurality of fasteners comprise a ceramic material.

7. The system of claim 1, further comprising a reinforcing ceramic insert positioned to surround each of the plurality of orifices in the sandwich panel.

8. The system of claim 7, further comprising a cup washer locking mechanism positioned to surround each of the plurality of orifices in the sandwich panel.

9. A method of assembling a stand-off panel thermal protection system, the method comprising:

attaching stand-off brackets to a base structure;

positioning a plurality of insulation components between and around the stand-off brackets;

attaching a sandwich panel to the stand-off brackets with a plurality of fasteners, the sandwich panel comprising;

a first ceramic matrix composite facesheet and a second ceramic matrix composite facesheet,

a ceramic matrix composite core positioned between the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet, the ceramic matrix composite core having a perimeter, the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet extending past the perimeter to form a gap surrounding the ceramic matrix composite core between the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet,

a plurality of orifices formed completely through the sandwich panel, and

a soft goods seal positioned in the gap,

wherein the first ceramic matrix composite facesheet is on the side of the sandwich panel closest to the base structure and the second ceramic matrix composite facesheet provides an outermost surface portion that is on the opposite side of the sandwich panel from the base structure, the fasteners being externally accessible at the outermost surface portion without removing a plug or other covering to access the fasteners.

10. The method of claim 9, wherein the sandwich panel comprises a cup washer locking mechanism positioned to surround each of the plurality of orifices in the sandwich panel, the method further comprising locking the fasteners in place with the cup washer.

11. The method of claim 9, wherein the base structure is an object chosen from one of a rocket, an aircraft or a spacecraft.

12. A flight vehicle, comprising:

a base structure; and

a stand-off panel thermal protection system, comprising;

a plurality of sandwich panels, each sandwich panel comprising;

a first ceramic matrix composite facesheet and a second ceramic matrix composite facesheet,

a ceramic matrix composite core positioned between the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet, the ceramic matrix composite core having a perimeter, the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet extending past the perimeter to form a gap surrounding the ceramic matrix composite core between the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet, and

a plurality of orifices formed completely through each sandwich panel;

a soft goods seal positioned in the gap of each sandwich panel;

a plurality of insulation components positioned between each sandwich panel and the base structure;

a plurality of stand-off brackets positioned between each sandwich panel and the base structure, the stand-off brackets being attached to the base structure; and

a plurality of fasteners positioned completely through the plurality of orifices to couple each sandwich panel to the plurality of brackets,

wherein the second ceramic matrix composite facesheet of each sandwich panel provides an outermost surface portion of the flight vehicle, the plurality of fasteners for each sandwich panel being externally accessible at the outermost surface portion without a plug or other covering for the fasteners.

13. The flight vehicle of claim 12, wherein the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet comprise at least one material chosen from oxide ceramic matrix composites or non-oxide ceramic matrix composites.

14. The flight vehicle of claim 12, wherein the ceramic matrix composite core is a truss core comprising at least one material chosen from oxide ceramic matrix composites or non-oxide ceramic matrix composites.

15. The flight vehicle of claim 12, wherein the soft goods seal comprises woven ceramic fabric and alumina fibrous batting insulation.

16. The flight vehicle of claim 12, wherein each of the plurality of standoff brackets comprise a ceramic matrix composite material or high temperature metallic material.

17. The flight vehicle of claim 12, wherein each of the plurality of fasteners comprise a ceramic material.

18. The flight vehicle of claim 12, further comprising a reinforcing ceramic insert positioned to surround each of the plurality of orifices in the sandwich panel.

19. A flight vehicle, comprising:

a base structure; and

a stand-off panel thermal protection system, comprising;

a plurality of sandwich panels, each sandwich panel comprising;

a first ceramic matrix composite facesheet and a second ceramic matrix composite facesheet,

a ceramic matrix composite core positioned between the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet, the ceramic matrix composite core having a perimeter, the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet extending past the perimeter to form a gap between the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet surrounding the ceramic matrix composite core, and

a plurality of orifices formed through each sandwich panel;

a soft goods seal positioned in the gap of each sandwich panel;

a plurality of insulation components positioned between each sandwich panel and the base structure;

a plurality of stand-off brackets positioned between each sandwich panel and the base structure, the stand-off brackets being attached to the base structure; and

a plurality of fasteners positioned through the plurality of orifices to couple each sandwich panel to the plurality of brackets,

wherein the brackets comprise a first angle and a second angle, the brackets being oriented so that if thermal expansion of the sandwich panels occur, the brackets bend so as to reduce the first angle and the second angle.

20. The flight vehicle of claim 19, wherein the plurality of fasteners comprise a ceramic material.